基本信息科学研究教育教学论文专著
基本信息
自1996年3月留校工作以来，一直从事叶轮机械气动热力学、航行体水动力学方向的教学与科研工作。

荣誉称号
2001年 获哈尔滨工业大学校部机关优秀共产党员

2003年 获哈尔滨工业大学优秀专兼职学生工作者

工作经历
1996.3~1997.12 哈尔滨工业大学能源科学与工程学院 助教

1997.12~1999.7 哈尔滨工业大学能源科学与工程学院 讲师

1999.7~2004.7 哈尔滨工业大学能源科学与工程学院 副教授

2004.7~至今 哈尔滨工业大学能源科学与工程学院 教授

2005.4~至今 哈尔滨工业大学能源科学与工程学院 博士生导师

2006.9~2015.1 哈尔滨工业大学能源科学与工程学院 副院长

2015.3~至今 哈尔滨工业大学能源科学与工程学院推进理论与技术研究所所长

教育经历
1988.9~1992.7 哈尔滨工业大学热力叶轮机械专业 本科1992.9~1997.12 哈尔滨工业大学热力叶轮机械专业 硕博连读


主要任职
“十一五”国家863计划重大项目“重型燃气轮机关键技术及系统”总体专家组专家

中国工程热物理学会理事

《工程热物理学报》第六届编委

《推进技术》第十三届编委

航天科技集团公司一院一部水下发射技术中心客座研究员

中船重工集团公司蒸汽动力系统国防重点实验室学术委员会委员

中国动力工程学会会员

《航空学报》、《机械工程学报》、《推进技术》、《Chinese Journal ofAeronautics》、《Propulsion and PowerResearch》评审

奖项成果

奖项名称巡航导弹发动机跨音速风扇高负荷弯扭叶片设计技术

获奖时间2008

完成人陈浮, 王仲奇

所获奖项国防科技进步二等奖



研究领域
叶轮机械气动热力学航行体水动力学 主要研究方向: 高效高负荷叶轮机械设计及其非定常分离流动控制机理；高温涡轮冷却流动机制及流场结构优化；叶轮机械三维流场实验及先进测试技术；气-固-液多相多场耦合流动仿真

团队成员



宋彦萍: 教授, 博士生导师 研究方向: 叶轮机械通流部分流动控制技术研究

刘华坪: 讲师 研究方向: 等离子体流动控制技术, 航行体水动力学

刘雷: 2011级博士研究生 研究方向: 高负荷风扇耦合控制技术研究

王云飞: 2012级博士研究生 研究方向: LES数值计算方法研究

俞建阳: 2012级博士研究生 研究方向: 等离子体流动控制技术

吴晓迪: 2013级博士研究生 研究方向: LES数值计算方法研究

郑振江: 2013级博士研究生 研究方向: 叶轮机械通流部分先进设计方法研究

李国占: 2014级博士研究生/2012级硕士研究生 研究方向: 等离子激励下气膜冷却流动研究

付云峰: 2015级博士研究生 研究方向: 高负荷涡轮叶栅叶顶泄露流动控制技术研究

马贵辉: 2015级博士研究生/2014级硕士研究生 研究方向: 水下航行体的流动控制技术

陈聪: 2016级博士研究生/2015级硕士研究生 研究方向: 射流式旋涡发生器流动控制技术

王坤: 2017级博士研究生 研究方向：涡轮叶栅内部流动不确定性研究

郝浩浩: 2017级博士研究生 研究方向：结构物出水

崔可: 2010级硕士研究生 研究方向: 航行体出筒以及水下运动的水动力研究

王睿: 2010级硕士研究生 研究方向: 压气机叶栅非对称端壁研究

杨学印: 2010级硕士研究生 研究方向: 管路典型附件的流动分析及优化设计

姚思楠: 2010级硕士研究生 研究方向: 串列叶栅对跨音速风扇性能的影响

朱凤琦: 2010级硕士研究生 研究方向: 低雷诺数条件下可压缩槽道湍流的大涡模拟

吕守庆: 2011级硕士研究生 研究方向: 临近空间高超声速飞行器引流涡轮装置气动设计

申丽辉: 2011级硕士研究生 研究方向: 航行体水下及出水过程的流体特性研究

余勇飞: 2011级硕士研究生 研究方向: 波浪的数值模拟及其流场结构分析

程肖岐: 2012级硕士研究生 研究方向: 射流式旋涡发生器对扩压叶栅端区流动的主动控制研究

郭玉杰: 2013级硕士研究生 研究方向: 不同密封结构对涡轮级性能影响的数值研究

李德雄: 2013级硕士研究生 研究方向: 微型离心压气机流场分析及其改型技术研究

黄星: 2014级硕士研究生 研究方向: 轴流压气机自循环引气及射流扩稳的数值研究

姜帅: 2015级硕士研究生 研究方向: 水下航行体流体动力学

孟睿: 2016级硕士研究生 研究方向：叶顶蜂窝结构

穆泽楠: 2016级硕士研究生 研究方向: 波浪仿真

李乐: 2017级硕士研究生 研究方向: 等离子体流动控制

郭峰: 2017级硕士研究生 研究方向: 叶轮机械气动热力学




讲授课程
空气动力学 能源科学与工程学院 本科生三年级空气动力学 航天学院飞行器设计与工程专业 本科生三年级叶片机原理 能源科学与工程学院飞行器动力工程专业 本科生四年级基于先进CFD技术的航空航天飞行器动力学仿真 本科生创新课实验空气动力学 能源科学与工程学院动力机械及工程专业 硕士研究生计算流体力学 能源科学与工程学院动力机械及工程专业 硕士研究生


招生信息
硕士招生:
每年招硕士研究生2名，研究方向是叶轮机械通流部分设计与流动分析、气-液-固多相多场耦合流动仿真等。

博士招生:
每年招博士研究生2名，研究方向是叶轮机械通流部分设计与流动分析、气-液-固多相多场耦合流动仿真等。

论文期刊

论文标题Numerical simulation of circulation control turbine cascade with Coanda jet and counter-flow blowing at high Mach numbers

作者Feng Yanyan, Song Yanping, Chen Fu

期刊名称The Aeronautical Journal

期卷121(1243):1239-1260

简单介绍The performance of a circulation-control inlet guide vane that makes use of the Coanda effect was studied numerically in a high Mach number turbine cascade. The effect of different shapes (elliptic and circular) of the Coanda surface at the blade trailing edge was investigated by implementing both a Coanda jet and a counter-flow blowing. Under high subsonic flow conditions, with a total blowing ratio of 3% of the mainstream, the circulation control cascade can reach the same performance as the reference stator with a 13.5% reduction in the axial chord length, with minimal increase of the energy loss coefficient. The Coanda surfaces with small curvature are more efficient in entraining the mainstream flow, and they achieve better aerodynamic performance. The wall attachment of the Coanda jet is improved by employing counter-flow blowing, resulting in a slight increase of both the exit flow angle and the expansion ratio. Under supersonic flow conditions at the cascade exit, it is more difficult for the circulation control cascade to reach the appropriate flow turning due to a premature shock wave, which is absent in the original cascade until the very end of the suction surface.


论文标题Flow Control on Bowed Compressor Cascades Using Vortex Generator Jet at Different Incidences

作者Li Longting, Song Yanping, Chen Fu, Meng Rui

期刊名称Journal of Aerospace Engineering

期卷30(5):1-14

简单介绍Vortex generator jets (VGJs) have been used to suppress the flow separations in bowed compressor cascades at different incidences via numerical calculations. The results show that with momentum injection and streamwise vortex produced by VGJ, the total losses in the bowed blades effectively decrease whereas the static pressure ratios increase. For the positively bowed blade, at -5° incidence, with slight flow separation, the mixing loss caused by VGJ is dominant and the loss increases by 1%; with an incidence ranging from 0° to t5°, the regions of the flow separations all decrease, and the total losses decrease by 2.7 and 5.4%, respectively; with the incidence increasing to t7°, the separation type converts from closed to open, and the loss decreases by 6.8%; when the incidence is t10°, one concentrated shedding vortex disappears, and the loss decreases by 9.27%. For the negatively bowed one, as the incidence increases from -5° to t7°, the flow separations are all effectively suppressed when all the separation types are closed, and the losses decrease by 2.9, 9.1, 17.5, and 19.75%, respectively. When the incidence increases to t10°, however, because of the huge range of flow separation, there is no improvement in the flow field, but the total loss increases by 1.37%.


论文标题Large Eddy Simulation of Saw Tooth Plasma Actuator for Improving Film Cooling Efficiency

作者Li Guozhan, Yu Jianyang, Chen Fu, Liu Huaping, Song Yanping, Li Linxi

期刊名称Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy

期卷231(5):357-370

简单介绍This paper presents results on a saw tooth plasma actuator for the inducement of flow topology and the improvement of flat plate film cooling efficiency. A phenomenological plasma model is constructed to generate the three-dimensional plasma force vectors of the saw tooth plasma actuator. The dynamics of airflow induced by the saw tooth plasma actuator on a flat plate in quiescent air are numerically investigated. The results show that the saw tooth plasma actuator pushes the fluids in all three directions and induces a three-dimensional jet flow with counter rotating streamwise oriented vortices that propagate downstream. The flow field characteristics of both cylindrical hole with and without the saw tooth plasma actuator are studied by large eddy simulation, and a comparison is made. The saw tooth plasma actuator improves the cold jet adherent performance and promotes the spanwise spreading rate of the coolant. Meanwhile, the streamwise vortices induced by the saw tooth plasma actuator suppress the development of counterrotating vortex pair, thus delaying the diffusion of coolant in the crossflow. Accordingly, the centerline cooling efficiency and the spanwise-averaged cooling efficiency are improved by 36% and 144% at x/d ？ 15, compared with the baseline case without the saw tooth plasma actuator.


论文标题A Saw tooth plasma actuator for film cooling efficiency enhancement of a shaped hole

作者Li Guozhan, Yu Jianyang, Liu Huaping, Chen Fu, Song Yanping

期刊名称Plasma Science and Technology

期卷19(8):1-13

简单介绍This paper reports the large eddy simulations of the effects of a saw-tooth plasma actuator and the laidback fan-shaped hole on the film cooling flow characteristics, and the numerical results are compared with a corresponding standard configuration (cylindrical hole without the saw tooth plasma actuator). For this numerical research, the saw-tooth plasma actuator is installed just downstream of the cooling hole and a phenomenological plasma model is employed to provide the 3D plasma force vectors. The results show that thanks to the downward force and the momentum injection effect of the saw-tooth plasma actuator, the cold jet comes closer to the wall surface and extends further downstream. The saw-tooth plasma actuator also induces a new pair of vortex which weakens the strength of the counter-rotating vortex pair (CRVP) and entrains the coolant towards the wall, and thus the diffusion of the cold jet in the crossflow is suppressed. Furthermore, the laidback fan-shaped hole reduces the vertical jet velocity causing the disappearance of downstream spiral separation node vortices, this compensates for the deficiency of the saw-tooth plasma actuator. Both effects of the laidback fan-shaped hole and the saw-tooth plasma actuator effectively control the development of the CRVP whose size and strength are smaller than those of the anti-counter rotating vortex pair in the far field, thus the centerline and the spanwise-averaged film cooling efficiency are enhanced. The average film cooling efficiency is the biggest in the Fan-Dc=1 case, which is 80% bigger than that in the Fan-Dc=0 case and 288% bigger than that in the Cyl-Dc=0 case.


论文标题Experimental and Numerical Study of Honeycomb Tip on Suppressing Tip Leakage Flow in Turbine Cascade

作者Fu Yunfeng, Chen Fu, Liu Huaping, Song Yanping

期刊名称ASME Turbo Expo 2017, Charlotte, NC USA

期卷ASME Paper GT2017-64942

简单介绍In this paper, the effect of a novel honeycomb tip on suppressing tip leakage flow in a highly-loaded turbine cascade has been experimentally and numerically studied. The research focuses on the mechanisms of honeycomb tip on suppressing tip leakage flow and affecting the secondary flow in the cascade, as well as the influences of different clearance heights on leakage flow characteristics. In addition, two kinds of local honeycomb tip structures are pro-posed to explore the positive effect on suppressing leakage flow in simpler tip honeycomb structures. Based on the experimental and numerical results, the physical processes of tip leakage flow and its interaction with main flow are analyzed, the following conclusions can be obtained. Honeycomb tip rolls up a number of small vortices and radial jets in regular hexagonal honeycomb cavities, increasing the flow resistance in the clearance and reducing the velocity of leakage flow. As a result, the structure of honeycomb tip not only suppresses the leakage flow effectively, but also has positive effect on reducing the associated losses in cascade by reducing the strength of leakage vortex. Compare to the flat tip cascade at 1%H gap height, the relative leakage flow in honeycomb tip cascade reduces from 3.05% to 2.73%, and the loss at exit section is also decreased by 10.63%. With the increase of the gap height, the tip leakage flow and loss have variations of direct proportion with it, but their growth rates in the honeycomb tip cascade are smaller. Consider the abradable property of the honeycomb seal, a smaller gap height is allowed in the cascade with honeycomb tip, and that means honeycomb tip has better effect on suppressing leakage flow. Two various local honeycomb tip structures has also been discussed. It shows that local raised honeycomb tip has better suppressing leakage flow effect than honeycomb tip, while local concave honeycomb tip has no more effect than honeycomb tip. Compare to flat tip cascade, the leakage flow in honeycomb tip cascade, local concave tip cascade and local raised honeycomb tip cascade decrease by nearly 17.33%, 15.51% and 30.86% respectively, the losses at exit section is reduced by 13.38%, 12% and 28.17% respectively.


论文标题Numerical study of the flow structures in flat plate and the wall-mounted hump induced by the unsteady DBD plasma

作者Yu Jianyang, Liu Huaping, Wang Ruoyu, Chen Fu

期刊名称Plasma Science and Technology

期卷19(1):57-63

简单介绍In this work, the dielectric-barrier-discharge plasma actuator was employed to study the flow structures induced by the plasma actuator over a flat plate and a wall-mounted hump. A phenomenological dielectric-barrier-discharge plasma model which regarded the plasma effect as the body force was implemented into the Navier–Stokes equations solved by the method of large eddy simulations. The results show that a series of vortex pairs, which indicated dipole formation and periodicity distribution were generated in the boundary layer when the plasma was applied to the flow over a flat plane. They would enhance the energy exchanged between the near wall region and the free stream. Besides, their spatial trajectories are deeply affected by the actuation strength. When the actuator was engaged in the flow over a wall-mounted hump, the vortex pairs were also produced, which was able to delay flow separation as well as to promote flow reattachment and reduce the generation of a vortex, achieving the goal of reducing dissipation and decreasing flow resistance.


论文标题Effect of Exhaust Angle on Evolutionary and Flow Characteristics of Pressure-equalizing Film on Surface of Underwater Vehicle

作者Chen Fu, Ma Guihui, Yu Jianyang, Jiang Shuai

期刊名称Journal of Ship Mechanics

期卷20(12):1495-1512

简单介绍Pressure-equalizing exhaust is an effective flow control technique to improve the hydrodynamic characteristics of underwater vehicles and to inhibit their pitching moment. In this paper, numerical simulation is conducted to study the underwater vertical movement process of an underwater vehicle with pressure-equalizing exhaust. The variation of the flow rate and velocity of the exhaust as well as the film length under different exhaust angles are given. The influence of the exhaust angle on the unsteady development of the pressure-equalizing film and the hydrodynamic characteristics of the flow field around the vehicle is analyzed. The topological structure is established for the flow field near and downstream the exhaust hole as well as the re-entrant jet field at the film tail. Besides, the shape feature and evolution of the pressure-equalizing film and its mechanism to reduce the pressure on the surface of underwater vehicles are discussed. The results are helpful for looking further into the physical nature of the improvement in the hydrodynamic characteristics of underwater vehicles by means of the pressure-equalizing exhaust technique.


论文标题Large Eddy Simulation of the Effects of Plasma Actuation Strength on Film Cooling Efficiency

作者Li Guozhan, Chen Fu, Li Linxi, Song Yanping

期刊名称Plasma Science and Technology

期卷18(11):1101-1109

简单介绍In this article, numerical investigation of the effects of different plasma actuation strengths on the film cooling flow characteristics has been conducted using large eddy simulation (LES). For this numerical research, the plasma actuator is placed downstream of the trailing edge of the film cooling hole and a phenomenological model is employed to provide the electric field generated by it, resulting in the body forces. Our results show that as the plasma actuation strength grows larger, under the downward effect of the plasma actuation, the jet trajectory near the cooling hole stays closer to the wall and the recirculation region observably reduces in size. Meanwhile, the momentum injection effect of the plasma actuation also actively alters the distributions of the velocity components downstream of the cooling hole. Consequently, the influence of the plasma actuation strength on the Reynolds stress downstream of the cooling hole is remarkable. Furthermore, the plasma actuation weakens the strength of the kidney shaped vortex and prevents the jet from lifting of the wall. Therefore, with the increase of the strength of the plasma actuation, the coolant core stays closer to the wall and tends to split into two distinct regions. So the centerline film cooling efficiency is enhanced, and it is increased by 55% at most when the plasma actuation strength is 10.


论文标题Numerical Study of the Effect of Honeycomb Tip on Tip Leakage Flow in Turbine Cascade

作者Fu Yunfeng, Chen Fu, Chen Cong, Song Yanping

期刊名称ASME Turbo Expo 2016, Seoul South Korea

期卷ASME Paper GT2016-56907

简单介绍A novel leakage flow control strategy with honeycomb seal applied on the tip of the rotor blades in a highly-loaded turbine cascade is proposed. The numerical method is used to study the tip leakage flow in a highly-loaded turbine cascades with flat tip and with honeycomb seal structure, the mechanism of honeycomb tip on inhibiting leakage flow is analyzed, the influence of various relative gap heights is also been investigated. The discussions of the action of the honeycomb-tip structure in reducing leakage flow and improving the turbine efficiency provide the according for control methods of tip leakage flow.


论文标题The Effects of Periodic Wakes on Boundary Layer Separation of Low-pressure Turbine Cascade Using Large Eddy Simulation

作者Wu Xiaodi, Chen Fu, Wang Yunfei

期刊名称ASME Turbo Expo 2016, Seoul South Korea

期卷ASME Paper GT2016-57205

简单介绍For low-pressure turbine, the unsteady disturbances are dominated by relative motions between rotors and stators and the unsteady flow is closely associated with aerodynamic efficiency of low-pressure turbine and engine performance. One of its most important manifestations is the boundary layer separation on the turbine blades by the passing wakes produced by upstream rows of blades. Hence, accurate prediction of the flow physics at low Reynolds number conditions is required to effectively implement flow control techniques which can help mitigate separation induced losses. The present paper concentrates on simulations for boundary layer separation of low-pressure turbine cascade under periodic wakes. In this paper, a multiblock computational fluid dynamics (CFD) code of compressible N-S equations is developed for predicting the phenomenon of boundary layer separation, transition and reattachment using large eddy simulation (LES) in the field of turbomachinery. The large-scale structures can be directly obtained from the solution of the filtered Naiver-Strokes equations and the small-scale structures are modeled by dynamic subgrid-scale model of turbulence. Firstly, unsteady boundary layer separation on a flat plate with adverse pressure gradient is simulated under periodic inflow. The time-averaged field, the phase-averaged field and the instantaneous flow field are presented and analyzed. The separation bubble becomes unstable and the location of transition moves back and forth due to vortex shedding. Secondly, a stator of turbomachinery which is influenced by wakes periodically passing is simulated. The results of the numerical simulations are discussed and compared with experimental data. For the instantaneous flow field, it seems that the spanwise vortices induced by upstream wakes are the primary reason of the initial roll-up of the shear layer and the Kelvin-Helmholtz instability plays an important role in the transition to turbulence which is observed in the separated flow.


论文标题Flow Control Investigation of Steady and Pulsed Jets in Bowed Compressor Cascades

作者Li Longting, Song Yanping, Chen fu, Liu Huaping

期刊名称ASME Turbo Expo 2016, Seoul South Korea

期卷ASME Paper GT2016-56855

简单介绍Based on the previous research about the combined flow control method which was carried out by applying the endwall steady VGJ to the bowed compressor cascades to reduce the secondary flow loss, for the consideration that the pulsed jets may save the mass flow required for control, therefore the unsteady VGJs over the different actuation frequencies and blowing ratios were investigated in detail. Under the conditions of same jet geometry parameters, the improvements to the fluid fields in the bowed compressor cascades caused by the pulsed jets are less than that induced by the steady cases. With the pulsed VGJ, for the positively bowed blade, the enhancement of the time-averaged aerodynamic performance can be achieved when the blowing ratio is greater than 0.6, but all of the unsteady conditions in this research can improve the flow field in the negatively bowed blade. The time-averaged total losses decrease by 1.6% and 7.0% at most for the positively and negatively bowed blades, respectively. The mechanisms by which the endwall pulsed vortex generator jets delay flow separation and reduce loss were explored. The results show that, being different from the single vortex produced in steady VGJ, the pulsed case generates a pair of streamwise vortices with the opposite sense of rotation. One vortex suppresses the development of the secondary flow, but the other one increases the size of the passage vortex. Furthermore, for the endwall pulsed VGJ, the changes of the blowing ratio plays a more important role in improving the flow fields in the bowed cascades than that of the actuation frequency.


论文标题Large Eddy Simulation of Film Cooling Flow Characteristics Based on Plasma Actuation

作者Li Guozhan, Yu Jianyang, Chen Fu, Li Linxi, Song Yanping

期刊名称52nd AIAA/SAE/ASEE Joint Propulsion Conference, Salt Lake City, Utah, USA

期卷AIAA 2016-5051

简单介绍Large eddy simulation (LES) was carried out to investigate the effect of plasma aerodynamic actuation on improving flat plate film cooling efficiency. In this work, a phenomenological model was adopted to provide the electric field generated by the plasma, resulting in the body force. Results show that with the downward plasma force, the penetration of the jet into the crossflow is suppressed and the jet trajectory is much closer to the wall in the vicinity of the cooling hole, so that the strength and the size of the counter-rotating vortex pair are decreased. The anti-kidney shaped vortex induced by the plasma actuation also weakens the strength of counter-rotating vortex pair. Furthermore, the plasma actuation adds energy into the boundary layer where the fluid is induced to accelerate, causing the disappearance of crossflow separation vortex pair downstream of the cooling hole, and then the turbulent kinetic energy in the recirculation zone is significantly reduced, so the film cooling efficiency is enhanced. When the plasma actuation strength is 5, the centerline and the spanwise-averaged film cooling efficiency are improved by 75% and 100% at most, compared with the baseline case.


论文标题Active Flow Separation Control on a Highly Loaded Compressor Stator Cascade with Synthetic Jets

作者Qin Yong, Wang Ruoyu, Song Yanping, Chen Fu, Liu Huaping

期刊名称ASME Turbo Expo 2016, Seoul South Korea

期卷ASME Paper GT2016-56830

简单介绍Numerical investigations on the control effects of synthetic jets are conducted upon a highly loaded compressor stator cascade. The influence of forcing parameters including actuation frequency, jet amplitude and slot location are analyzed in detail with the single-slit synthetic jet. Besides, a new slot arrangement is put forward for the purpose of effectively controlling flow separation. Simulation results validate the remarkable effectiveness of the single-slit synthetic jet on controlling flow separation. Owing to the coupling effect between the jet and the main flow, the actuation appears to be most efficient under the characteristic frequency of the main flow passing through the airfoil. Additionally, with the increase of jet momentum coefficient, the control effect is enhanced at first and then decreased, depending on the two aspects: the improvements of aerodynamic performance by momentum injection and the additional flow losses caused by the jet. Compared to other actuator configurations, the segment synthetic jet with three sections can more effectively deflect the endwall cross flow and thus impede the development of corner vortex, which helps to restrain the accumulation of low momentum fluid towards the corner, emphasizing the importance of slot arrangement. Accordingly, under the optimum condition, the total pressure loss coefficient gains a 15.8% reductions and the static pressure rise coefficient is increased by 5.01%.


论文标题Numerical Investigation and Quantitative Loss Analysis of Typical Wet Steam Spontaneous Condensation Based on Two Fluid Model

作者Cui Ke, Song Yanping, Chen Huanlong, Chen Fu, Ooyama Hiroharu

期刊名称Heat and Mass Transfer

期卷52(7):1329-1342

简单介绍A two-fluid model with the influence of inter-phase velocity-slip taken into account is proposed and a modified realizable k–ε turbulence model is put forward as well to make the equation set of two-fluid model closed. Based on this two-fluid model, numerical simulations are implemented on typical wet steam flow in different cases. Good consistency between numerical result and the experimental result implies that this two-fluid model is provided with high accuracy and wide applicability. The flow field analysis also shows that there exist several particular sites along the flow direction. These particular sites could illustrate the development mechanism of nucleation and droplet growing. In addition, further discussion about the flow in cascade then indicates that the presence of condensation has strong impact on the flow while the impact of inter-phase velocity-slip is relatively weaker. The composition of total pressure loss is present here, the majority of total pressure loss brought by condensation is about 8.78% of inlet total pressure while the inter-phase velocity-slip just results in a small part of about 0.42% of inlet total pressure, the rest of the total pressure loss is caused by pneumatic factors and this part is about 3.95% of inlet total pressure.


论文标题Numerical investigation on influence of suction in S-shaped inlet to the rear fan-stage performance

作者Yu Jianyang, Liu Huaping, Liu Lei, Li Guozhan, Chen Fu, Song Yanping

期刊名称52nd AIAA/SAE/ASEE Joint Propulsion Conference, Salt Lake City, Utah, USA

期卷AIAA 2016-5055

简单介绍Numerical simulations of the whole structure of the air intake and the fan stage were conducted to explore the evolution process of a half flush-mounted air intake exit distortion in the rear components. In this investigation, a scheme of suction control imposed near the throat of the inlet was carried out to realize the large boundary layer ingestion. The results indicate a slight improvement in the aerodynamic performance of the fan stage after the suction, when it was operated in the prototype condition compared with the uniform air condition. The distorted region at the air intake exit decreases significantly as well. In addition, the low energy fluid gathering at the bottom cross section is decreasing while moving to the tip station of the rotor hub. Resulting in a covering about 3 blade passages at the rotor blade front edge was found in the end. Both the total pressure and velocity of the air in these distorted blade passages are lower but more after the suction than those in other passages. However, serious flow separations occur at the stator blade suction side in the influence of the large boundary ingestion in the prototype condition. And they mainly happen at the 50% span and weaken with the suction.


论文标题Numerical Study of Fluid Dynamics and Heat Transfer Induced by Plasma Discharges

作者Yu Jianyang, Chen Fu, Liu Huaping, Song Yanping

期刊名称Plasma Science and Technology

期卷17(1):41-49

简单介绍A numerical investigation is conducted to explore the evolution of a plasma discharge and its interaction with the fluid flow based on a self-consistent fluid model which couples the discharge dynamics with the fluid dynamics. The effects of the applied voltage on the distribution of velocity and temperature in initially static air are parametrically studied. Furthermore, the spatial structure of plasma discharge and the resulting force contours in streamwise and normal directions are discussed in detail. The result shows that the plasma actuator produces a net force that should always be directed away from the exposed electrode, which results in an ionic wind pushing particles into a jet downstream of the actuator. When the energy added by the plasma is taken into account, the ambient air temperature is increases slightly around the electrode, but the velocity is almost not affected. Therefore it is unlikely that the induced flow is buoyancy driven. For the operating voltages considered in this paper, the maximum induced velocity is found to follow a power law, i.e., it is proportional to the applied voltage to the 3.5 power. This promises an efficient application in the flow control with plasma actuators.


论文标题Numerical Investigation on Impact of Blowing Control in a Flush-mounted S-shaped Inlet to Rear Fan-stage Performance

作者Liu Lei, Chen Fu, Song Yanping, Chen Huanlong, Yu Jianyang

期刊名称Proceedings of the Institution of Mechanical Engineers, Part G, Journal of Aerospace Engineering

期卷28(2):162-167

简单介绍In this paper, numerical simulation of the whole structure of a half flush-mounted S-shaped airintake and the rear fan stage was conducted for investigating the impact of airintake exit distortion on the fan stage performance. Considering substantial boundary layer ingesting, a scheme of blowing control imposed near the first bend of the inlet where the flow separation occurs was also carried out. The results show that the air intake internal separation is eliminated and the distorted air region at its exit decreases significantly after blowing, simultaneously, the aerodynamic performance of the rear fan-stage improves dramatically. The choked mass flow increases about 1.45%, and the maximum isentropic efficiency as well as the corresponding total pressure ratio at this point increases about 1.83% and 1% respectively. In addition, the distorted fluid always covers several blade passages no matter with blowing control or not when it goes through the fan-stage. Both relative total pressure and velocity of air in these distorted blade passages are lower than that in other uniform passages and have slightly increased with blowing. Under effect of the inlet flow angle increase caused by the non-uniform air admission and the adverse pressure gradient in the rear part of the flow passage, serious flow separation occurs at the stator blade suction side but mainly exists at 50% span and below and weakens after blowing control.


论文标题Investigation of the Flow Structure on a Flat Plate Induced by Unsteady Plasma Actuation with DNS Methods

作者Yu Jianyang, Chen Fu, Liu Huaping, Song Yanping

期刊名称Plasma Science and Technology

期卷17(12):1032-1037

简单介绍An investigation into the flow characteristic on a flat plate induced by an unsteady plasma was conducted with the methods of direct numerical simulations (DNS). A simplified model of dielectric barrier discharge (DBD) plasma was applied and its parameters were calibrated with the experimental results. In the simulations, effects of the actuation frequency on the flow were examined. The instantaneous flow parameters were also drawn to serve as a detailed study on the behavior when the plasma actuator was applied to the flow. The result shows that induced by the unsteady actuation, a series of vortex pairs which show dipole formation and periodicity distribution are formed in the boundary layer. The production of these vortex pairs indicates a strong energy exchange between the main flow and the boundary layer. They move downstream under the action of the free stream and decay under the influence of the fluid viscosity. The distance of the neighboring vortices would be ignored when the actuation frequency is too small to make a difference.


论文标题Effect of Endwall Vortex Generator Jets on Flow Separation Control in a Linear Compressor Cascade

作者Feng Yanyan, Song Yanping, Chen Fu, Liu Huaping

期刊名称Proceedings of the Institution of Mechanical Engineers, Part G, Journal of Aerospace Engineering

期卷229(12):2221-2230

简单介绍As a 50° camber angle compressor cascade being the object, the numerical investigations of the endwall vortex generator jets effect on flow separation control were conducted. The results show that the flow separation is significantly weakened and the maximum total pressure loss reduction is 9.5% at Mach number 0.23. When the cascade inlet Mach number is 0.71, more benefit is obtained and the total pressure loss is reduced by up to 14.8%. A primary streamwise vortex is produced by the interaction of endwall jet with the coming flow. This vortex could restrain the transverse movement of the endwall secondary flow and entrain high energy fluid of the mainstream to the corner region. Both of the aspects are of benefits for the flow momentum increasing in the corner region. Thus the flow separation is suppressed efficiently. The location and intensity of the streamwise vortex are important to the performance of vortex generator jet. For the object investigated in this paper, the proper jet location is around 10% axial chord length before the cascade and meanwhile close to the suction surface. To avoid strong mixing losses, the intensity of the streamwise vortex is suggested be moderate.


论文标题Numerical Method for Non-Equilibrium Phase Transition in Low Pressure Stage of Steam Turbine

作者Cui Ke, Song Yanping, Chen Huanlong, Chen Fu

期刊名称Journal of the Brazilian Society of Mechanical Sciences and Engineering

期卷37(4):1-11

简单介绍Based on the classical droplet nucleation theory along with the droplet growing model, a dual-fluid model considering the effect of velocity-slip between the liquid phase and the gaseous phase is proposed in this paper. Both 2-D and 3-D numerical simulations were then implemented, respectively, on the flow in low pressure cascade and the result showed that this dual-fluid model was provided with relatively high resolution and good reliability on capturing the typical flow characteristics, such as the “Wilson Point” and the “Condensing Shock”. In addition, both of the 2-D investigation and 3-D investigation implied that the non-equilibrium condensation had great impact on the parameter distribution as well as the loss of the flow field. Meanwhile, because the radius of droplets generated during the condensation might be quite small, the velocity-slip between the liquid phase and the gaseous phase almost has no influence on the flow field compared with condensation.


论文标题Active Flow Separation Control Using Endwall Vortex Generator Jets in Highly Loaded Compressor Cascades

作者Feng Yanyan, Song Yanping, Chen Fu, Liu Huaping

期刊名称ASME Turbo Expo 2015, Motreal Canada

期卷ASME Paper GT2015-42268

简单介绍An active flow control technique of endwall vortex generator jets (VGJs) was used in two kinds of highly loaded compressor cascades. Numerical investigations were carried out on a NACA 65 profile with a large camber angle at low subsonic and high subsonic speeds, and a CDA profile at high subsonic speed respectively. The results indicate that the endwall VGJs can restrain flow separation effectively by reenergizing the boundary layer fluids and resisting the transverse movement of endwall low energy fluid. At Mach number 0.23, the results of the jet blowing ratio study illustrate that the increasing jet velocity shows noteworthy potential to improve the cascade aerodynamic performance. The double jets structures gains weaker beneficial effects than single jet. It is attributed to the complex flow structure, leading to heavy disturbance and large-scale mixing loss. Under variable angles of attack, the loss coefficients are maximally reduced by 4.1%, 9.5% and 17.3% under -5°, 0° and +5° angles of attack respectively. Under high subsonic conditions, the endwall VGJs still has significantly positive effects on NACA 65 profile. Considering the small separation region of CDA, the loss coefficients are slightly increased although the flow separation is weaken further by VGJ.


论文标题Effects of Vortex Generator Jet on Flow Separation in Bowed Compressor Cascades

作者Li Longting, Song Yanping, Chen Fu, Liu Huaping

期刊名称ASME Turbo Expo 2015, Motreal Canada

期卷ASME Paper GT2015-42308

简单介绍A combined flow control is performed by analyzing the influence of vortex generator jet (VGJ) which is installed on the endwall of blade due to the operating simplicity on flow separation in bowed compressor cascades with high loading. Loss measurements are taken over a wide range of parameters including jet mass flow, jet direction and jet location to determine their effectiveness in controlling flow separation. The results indicate that there are optimal jet parameters which attain the largest total pressure loss reduction up to 2.7% and 9.1% for positively and negatively bowed blade respectively. The topological principles of cascade surfaces are applied to analyze the three-dimensional separation flow of the bowed blades to gain a further insight into the mechanism of loss reduction through VGJ. The consequences show that the VGJ can produce a streamwise vortex forcing the passage vortex to move in the direction away from suction side thus not inducing the low-energy fluid on suction side to separate any more. Moreover, a separation line is left on blade endwall when the streamwise vortex departs from it, which forms a barrier on the endwall hampering the migration of boundary layer from pressure side to suction side caused by cross pressure gradient so that the size of passage vortex decreases simultaneously. For positively bowed blade，the separation type on suction side is open separation with relatively low loss as a result of the migration of boundary layer from endwall to midspan of cascade, so the flow separation in corner region is not so severe that the improvement effect by VGJ is slight. The separation on suction side vanished basically with influence of VGJ. The separation type on suction side of negatively bowed blade belongs to closed separation characterized by a separation line beginning with saddle point and ending up with separation spiral point for the reason that opposite migration direction of boundary layer compared with positively bowed blade, which will cause larger loss. After affected by VGJ, the corner vortex disappears and the strength as well as the size of concentrated shedding vortex reduces by the fluid from jet tube applying momentum to the low-energy fluid in the corner region.


论文标题Numerical Study on Typical Wet Steam Flow Based on a New Two-fluid Model

作者Cui Ke, Chen Huanlong, Song Yanping, Chen Fu

期刊名称ASME Turbo Expo 2015, Motreal Canada

期卷ASME Paper GT2015-42361

简单介绍A new two-fluid model with the influence of inter-phase velocity-slip taken into account was proposed and a modified realizable k-？？turbulence model was put forward as well to make the equation set of two-fluid model closed. Based on this two-fluid model, numerical simulations were conducted on typical wet steam flow in different cases. The good consistency of numerical result and the experimental result infers that this two-fluid model is provided with high accuracy and wide applicability. The flow field analysis also shows that there exist several particular positions along the flow direction. These particular positions illustrate the development mechanism of nucleation and droplet growing. In addition, further discussion on the flow in cascade then indicates that the occurrence of condensation has strong impact on the flow while the impact of inter-phase velocity-slip is relatively weaker. The composition of total pressure loss is present here, the majority of total pressure loss brought by condensation is about 8.78% of inlet total pressure while the inter-phase velocity-slip just results in a small part of about 0.42% of inlet total pressure, the rest of the total pressure loss is caused by pneumatic factors and this part is about 3.95% of inlet total pressure. In addition, discussion about the turbulence then shows that the turbulence intensity in two-phase flow is higher than that in single-phase flow.


论文标题Large Eddy Simulation of Boundary Layer Separation and Reattachment in a LPT Blade at Different Incidence Angles

作者Wang Yunfei, Liu Huaping, Song Yanping, Chen Fu

期刊名称ASME Turbo Expo 2015, Motreal Canada

期卷ASME Paper GT2015-42264

简单介绍In order to predict the phenomenon of laminar flow separation, transition and reattachment in a high-lift low pressure turbine (LPT), a self-developed large eddy simulation program to solve three dimensional compressible N-S equations was used to simulate the flow structures in T106A LPT blade passage. The outlet Mach number is 0.4 and the Reynolds number is 1.1？105 based on the exit isentropic velocity and the axial chord. The distributions of the time-averaged static pressure coefficient, kinetic loss coefficient and wall shear stress on the blade surface at +7.8？？incidence angle agree well with the results of experiment and direct numerical simulation (DNS). The locations of laminar separation and reattachment point occur around 83.6% and 97% axial chord respectively. The evolutionary process of spanwise vorticity and large-scale coherent structure near the trailing edge on the suction side in one period indicates that the two-dimensional shear layer is gradually unstable as a result of spanwise fluctuation and Kelvin-Helmholtz (K-H) instability. The boundary layer separates from the suction surface and the hairpin vortex appears in succession, which leads to transition to turbulence. Analysis of the incidence angle effect on the boundary layer separation point as well as separation bubble scale was also performed. A small scale separation bubble exists around the leading edge at positive incidences. As the incidence angle changes from positive to negative, the separation bubble near the leading edge disappears and the boundary layer thickness reduces gradually. The separation point at the rear part of suction side moves downstream, yet the reattachment point barely changes. The Reynolds stress and turbulent kinetic energy profiles change dramatically at zero and positive incidence. This illustrates that the incidence angle has great influence on the development of the boundary layer and the flow field structures.


论文标题Numerical Investigation on Impact of A Flush-mounted Airintake Exit Distortion to the Rear Fan Performance

作者Liu Lei, Chen Huanlong, Chen Fu, Song Yanping

期刊名称ASME Turbo Expo 2014, Düsseldorf Germany

期卷ASME Paper GT2014-26442

简单介绍For the sake of investigating impact of inlet distortion on the fan stage performance, numerical simulation of the whole structure of a flush-mounted S-shaped inlet and the rear fan stage was conducted in this paper. The single fan stage with uniform air admission was researched at the same time for comparison. Considering substantial boundary layer ingesting, a scheme of suction control imposed at the first bend of the inlet was also carried out. The results show that the total pressure ratio as well as the efficiency of the fan stage decreases dramatically and the choked mass flow has a reduction about 1.20% as compare with the uniform air condition. With suction control, aerodynamic performance of the fan stage improves slightly, the choked mass flow and total pressure ratio at the maximum isentropic efficiency point increase about 0.28% and 0.25% respectively, and the stable operation range is extended.With effect of rotating rotor, the significant low energy region at bottom of the airintake exit decrease continually as it travels downstream to the rotor and covers nearly three flow passages at the front-edge rotor blade, moreover, the high-energy fluid mixes with the low-energy fluid.


论文标题Investigation of the DBD Plasma Effect on Flat Plate Flow

作者Yu Jianyang, Liu Huaping, Xu Dimeng, Chen Fu

期刊名称Plasma Science and Technology

期卷16(3):197-202

简单介绍Particle image velocimetry experiments and simulations were conducted in this study to clarify the influence of the DBD plasma actuator on the flow over a flat plate. The result shows that the actuator not only effectively leads to a local rise in near-wall velocity, but also efficiently causes a decrease in the displacement thickness of the boundary layer. Actuator-induced vorticity is generated to intensify the energy exchange between the main flow and the boundary layer, and dynamic energy is thus added directly to the low-energy fluid by the actuator. Although the increase in fluid velocity also brings a rise in dynamic energy loss, the energy added by the actuator can cover this to provide growth in the energy of the boundary layer. The plasma actuator presents a better performance when the free-stream velocity is lower.


论文标题2D Simulation of Circulation Control Turbine Cascade

作者Song Yanping, Li Yachao, Chen Huanlong, Chen Fu

期刊名称Proceedings of the Institution of Mechanical Engineers, Part G, Journal of Aerospace Engineering

期卷225(7):761-767

简单介绍The application of Coanda effect to turbine was first studied in this paper through two-dimensional numerical simulation of circulation control turbine cascades. The influence of the aerodynamic and geometric parameters, such as the supply pressure of jet, the slot height, the shape and curvature of the Coanda surface, on the performance of the circulation control turbine cascade was investigated in detail. The results show that the circulation control turbine cascade can achieve and exceed the performance level of the original turbine cascade (the baseline) at the cost of an acceptable jet supply pressure. The aerodynamic performance of circulation control turbine cascades is largely determined by two critical factors: the velocity of jet and the curvature of the Coanda surface. Low magnitude of jet velocity and large curvature of Coanda surface near the jet exit would lead to a serious jet detachment that is generally responsible for less flow turning and high energy loss. The jet attachment to the Coanda surface with a large curvature can be obtained only when the jet speed is high enough. And at this time circulation control turbine cascade can bring a large flow turning but also a high energy loss based on a modified definition of the energy loss coefficient.


论文标题Effects of Boundary Layer Suction on Aerodynamic Performance in a High-load Compressor Cascade

作者Guo Shuang, Chen Shaowen, Song Yanping, Song Yufei, Chen Fu

期刊名称Chinese Journal of Aeronautics

期卷23(2):179-186

简单介绍This article is aimed to experimentally validate the beneficial effects of boundary layer suction on improving the aerodynamic performance of a compressor cascade with a large camber angle. The flow field of the cascade is measured and the ink-trace flow visualization is also presented. The experimental results show that the boundary layer suction reduces losses near the area of midspan in the cascade most effectively for all suction cases under test. Losses of the endwall could remarkably decrease only when the suction is at the position where the boundary layer has separated but still not departed far away from the blade surface. It is evidenced that the higher suction flow rate and the suction position closer to the trailing edge result in greater reduction in losses and the maximum reduction in the total pressure loss accounts to 16.5% for all cases. The suction position plays a greater role in affecting the total pressure loss than the suction flow rate does.


论文标题Experimental Study of Bowed-twisted Stators in an Axial Transonic Fan Stage

作者Chen Fu, Li Shaobin, Su Jiexian, Wang Zhongqi

期刊名称Chinese Journal of Aeronautics

期卷22(4):364-370

简单介绍Bowed-twisted stators with large camber angles have been developed to replace the conventional tandem stators in an axial transonic fan stage working at high subsonic speeds. Experimental study is carried out on both stages with tandem stators and with bowed-twisted stators. Compared to the tandem stators, the bowed-twisted stators change the distribution of the low-energy fluid and the potential high-energy fluid at the compressor outlets, reduce the endwall loss significantly, improve the aerodynamic matching of rotors and stators, and eventually increase the fan stage performances. The aerodynamic performances of the fan stage at different operating points are compared and contrasted. The results show that the transonic fan stage with bowed-twisted stators has better aerodynamic performances. It is thus suggested that the bowed-twisted stators with large camber angles be popularized into the high-loaded transonic fan designs.


论文标题Enhancing Aerodynamic Performances of Highly Loaded Compressor Cascades via Air Injection

作者Feng Dongmin, Chen Fu, Song Yanping, Chen Huanlong, Wang Zhongqi

期刊名称Chinese Journal of Aeronautics

期卷22(2):121-128

简单介绍This article experimentally studies the effects of air injection near the blade trailing edge on flow separation and losses in a highly loaded linear compressor cascade. Aerodynamic parameters of eight cascades with different air injection slot configurations are measured by using a five-hole probe at the cascade outlets. Ink-trace flow visualization is performed to obtain the flow details around the air injection slots. The static pressure distribution is clarified with pressure taps on the endwalls. The results indicate that air injection has little effect on the static pressure distribution on the endwalls, but improves the flow behavior at the corners between the suction surfaces and the endwalls with the decrease in losses at midspan. Slot positions have great effect on the compressor cascade performances. The optimal slot location is 25% of the blade span. The energy loss coefficient is reduced by 5.5% at most.


论文标题Flow Field Improvement by Bowed Stator Stages in a Compressor with Different Axial Gaps under Near Stall Condition

作者Lu Huawei, Chen Fu, Wan Jilin, Wang Zhongqi

期刊名称Chinese Journal of Aeronautics

期卷21(3):215-222

简单介绍The outlet flow fields of a low-speed repeating-stage compressor with bowed stator stages are measured with five-hole probe under the near stall condition when the rotor/stator axial gap varies. The performances of the straight stator stages are investigated and compared to those of the bowed stator stages. The results show that using bowed stator stages could alleviate the flow separation at both upper and low corners of the suction surface and the endwalls, and decrease the losses along the flow passage as well as the outlet flow angle. As the rotor/stator axial gap decreases, although the diffusion capacity of the compressor increases obviously, the outlet flow field in the straight stator stages deteriorates quickly. By contrast, little changes occur in the bowed stator stages, indicating that as the rotor/stator axial gap decreases, improved performance is achieved in the bowed stator stages.


论文标题Effects of Air Injection on Performance of Highly-loaded Compressor Cascades

作者Song Yanping, Chen Huanlong, Chen Fu, Wang Zhongqi

期刊名称ASME Turbo Expo 2007, Motreal Canada

期卷ASME Paper GT2007-27062

简单介绍The effects of air injection on the performance of highly-loaded straight blade compressor cascade and compound lean blade cascade were investigated numerically. Air injection was implemented via the hole/slot penetrating through the pressure and suction surfaces under the effect of the pressure difference between the two sides. Various injection configurations including one-hole, multi-hole and slot configurations were studied in the straight blade cascade first to find the optimum injection configuration in this case. Then the mechanism of the injection slot on the performance improvement of the straight blade cascade was discussed in detail. The results show that the optimum radial location of the injection slot is closely related to the flow pattern, especially the location of the saddle point as well as the spiral point in the corner region. These locations therefore should be determined in order to eliminate the spiral point in the corner region and at the same time control the saddle point effectively. When the radial width of the slot is 4.0mm, the through-flow capacity is increased by 1.59% with a 22.15% reduction in total loss. This is the slot configuration that has the most favorable effects on the cascade total loss reduction and flow behavior improvement in the endwall/suction surface corner among the three configurations studied in this paper. The effects of air injection on the performance improvement in the compound lean blade cascade are less significant than those in the straight blade cascade though the compound lean blade cascade with the injection slot has the most improvement in the aerodynamic performance when the slot is placed at an appropriate location in this study.


论文标题Effects of Compound-Lean Stator Clocking in a Low-Speed Axial Compressor

作者Chen Fu, Gu Zhonghua, Xie Haiyi, Wang Zhongqi

期刊名称AIAA Journal of Propulsion and Power

期卷22(6):1424-1426

简单介绍The experimental investigation into the effects of stator clocking on the performance in a low-speed repeating stage axial compressor with compound-lean stators show that stator clocking has a significant effect on the compressor efficiency, and the effect becomes pronounced as the mass flow rates increase. At the design condition, the maximum variation of efficiency is 0.6% due to stator clocking effect while 2.7% at the maximum mass flow rate condition. The main reason for the variation of the compressor efficiency as the clocking positions vary is that the upstream stator wakes enter the following passage at different circumferential positions, and then mix with the low energy fluid in the following passage.


论文标题Experimental Study of Stator Clocking Effects in an Axial Compressor

作者Chen Fu, Gu Zhonghua, Lu Huawei, Wang Zhongqi

期刊名称Chinese Journal of Aeronautics

期卷19(4):278-285

简单介绍This paper is focused on the experimental study of the effects of stator clocking on the performance of a low-speed repeating stage axial compressor with compound-lean stators as well as the one with conventional stators (the baseline) for comparison. The experimental results show that as the clocking positions vary, the upstream stator wake enters the following passage at different circumferential positions, and then mixes with the local fluid in the following passage. This is the main reason for the variation of the compressor performance resulted from the stator clocking effects. The variation of the compressor performance due to the clocking effect is less pronounced for the compressor with compound-lean stators than with the baseline. At a certain clocking position, the efficiency of the compressor with compound-lean stators is increased in comparison with that of the baseline，especially on small mass flow rate conditions, e.g., 0.7% at design condition and 3.5% at near-surge condition in this case. The maximum 1.22% and the minimum 0.07% increases in efficiency on design condition are obtained through the combined effects of the stator compound-lean and the stator clocking in this case.


论文标题Effects of Boundary Layer Suction on the Performance of Compressor Cascades

作者Chen Fu, Song Yanping, Chen Huanlong, Wang Zhongqi

期刊名称ASME Turbo Expo 2006, Barcelona Spain

期卷ASME Paper GT2006-90082

简单介绍The effects of boundary layer suction on the aerodynamic performance of compressor cascade are mainly determined by: (1) the location of the suction slot; (2) the suction flow rate; (3) the suction slot geometry; and (4) the aerodynamic parameters of the cascade (e.g. solidity and incidence). In this paper, an extensive numerical study has been carried out to investigate the effects of these influencing factors in a highly-loaded compressor cascade by comparing the aerodynamic performance of the cascade in order to give guidance for the application of boundary layer suction to improve the performance of modern highly-loaded compressors. The results show that boundary layer suction alleviates the accumulation of low-energy fluid at suction surface corners and enhances the ability of flow turning, and this improvement in flow behavior depends on the location of the suction slot and the suction flow rate. When the location of the suction slot and the suction flow rate are fixed, as the cascade solidity decreases from 1.819 to 1.364 and 1.091, the cascade total pressure loss is reduced at most by 25.1%, 27.7% and 32.9% respectively, and the cascade exit flow deviation is decreased by 3.1°, 4.2° and 5.0° accordingly. Moreover, boundary layer suction also has the largest effect in the cascade with smaller solidity at large positive incidences, which means that boundary layer suction is an effective way to widen the stable operating range of the highly-loaded compressor cascade. The suction slot geometry is described by the suction slot width and the suction slot angle with respect to the direction normal to the blade suction surface. The results show that the flow behavior is improved and the endwall loss is reduced further as the increase of the suction slot width. The suction slot angle has an obvious influence on the pressure inside the slot, therefore, should be considered in the design of the suction slot since the maximum pressure inside the slot is usually required.


论文标题A Numerical Investigation of Boundary Layer Suction in Compound Lean Compressor Cascades

作者Song Yanping, Chen Fu, Yang Jun, Wang Zhongqi

期刊名称ASME Journal of Turbomachinery

期卷128(2):357-366

简单介绍This paper is focused on the numerical investigation of boundary layer suction (BLS) via a slot on the suction surfaces of two compound lean compressor cascades with large camber angles as well as a conventional straight compressor cascade for comparison. The objective of the investigation is to study the influence of boundary layer suction on the performance of compound lean compressor cascades, thus to discuss the possibility of the application of boundary layer suction to improve their performance. An extensive numerical study has been carried out under different spanwise lengths and different axial positions of the slots, and different suction flow rates. The results show that the total loss of all three cascades is reduced significantly by boundary layer suction, and the largest reduction occurs at the highest suction flow rate. The axial locations of the slot have little effect on the total loss of the three cascades, which means the slots are opened within the optimal axial range in this case. The slot opened along the full span is the best one to obtain the largest reduction in total loss for all three cascades due to the alleviation of flow separation in the corner between the endwall and the suction surface. Moreover, the flow turning is increased, and pressure rise at the rear of the passage is recovered along the whole blade height via boundary layer suction along the full span, enhancing the working range of the highly loaded compressor cascades.


论文标题Effect of Turning Angle on Flow Field Performance of Linear Bowed Stator in Compressor at Low Mach Number

作者Zhang Yongjun, Chen Fu, Feng Guotai, Su Jiexian

期刊名称Chinese Journal of Aeronautics

期卷19(4):271-277

简单介绍A comparison of the results of a computational simulation and an experimental measurement indicates a good agreement between them: the bowed blade lowers the energy loss coefficient of engine by 11% in the simulation and by 13% in the measurement. To further discuss the application conditions of bowed blade in compressor, with incidence equal to zero and other boundary conditions unchanged, a computational investigations on four series of linear stators with different airfoil turning angles are achieved. It is found that the bowed blade has much positive effect in high airfoil turning angle cascade, for example, the optimal retrofit of 30°bow angle highly reduces the energy loss coefficient by 17.9%, when the airfoil turning angle is 59.5°. But the optimal retrofit of 15° has only 0.7% reduction when the airfoil turning angle is 39.5°, or even the compressor performance will get worse with the bow angle gradually increasing. Consequently, it is verified that the turning angle is one of the important factors to decide whether to apply the bowed blade into compressor at low Mach number.


论文标题An Experimental Study of Film Cooling in a Negatively Bowed Cascade with a Large Turning Angle

作者Chen Fu, Yang Ke, Song Yanping, Wang Zhongqi

期刊名称Heat Transfer—Asian Research

期卷34(1):1-8

简单介绍Transverse measurements are carried out at the outlet of the straight and negatively bowed turbine cascades with a 106？ turning angle respectively with and without cooling air injection. The air injection is from single or multiple rows of ten holes (26 schemes in all). Experimental results show that the negatively bowed cascade produces more energy loss than the straight one without cooling air injection. Cooling air injection from the holes on both the pressure and the suction surface near the trailing edge can reduce energy losses in both the straight and the negatively bowed cascades. The increase in loss is less in the negatively bowed cascade than that in the straight one with cooling air injection from holes of multiple rows at the leading edge, whereas cooling air injection from holes of multiple rows at the trailing edge reduces the energy loss in the negatively bowed cascade.


论文标题Optimization Design of Compressor Cascade with Swept and Curved Blades

作者Zhao Guijie, Chen Fu, Song Yanping, Wang Zhongqi

期刊名称43rd AIAA Aerospace Sciences Meeting and Exhibit, Reno, Nevada, USA

期卷AIAA 2005-336

简单介绍A unique blade integrating forward-sweep with positive-curve shortly named SCB was designed to test if the positive effects of sweep and dihedral can be combined in one configuration. Two cascades including the straight and the swept-curved cascades have been experimentally studied. Aerodynamic parameters of the two cascades were measured by a five-hole probe at several different positions and ink trace flow visualization was conducted on blade surfaces. Based on the experimental results, a hybrid optimization approach was introduced to search the optimal compressor blade stacking line. The sweep angle (height) and curve angle (height) were treated as design variables of the SCB stacking line. Uniform Design of Experiment (UDOE) was firstly employed to explore the samples which uniformly distributed in the design space. The commercial CFD solver-FLUET was used to simulate the turbulence flow and obtain the overall aerodynamic parameter of the samples. The quadratic Response Surface Model (RSM) for approximation was constructed to express the relationship between the design variables and the overall aerodynamic parameters. Then the Genetic Algorithms (GAs) was applied for global exploration to achieve the optimal matching of sweep and curve. Compared with the experiment blade, the optimization results demonstrated the feasibility, validity, robustness and timesaving of this approach and aerodynamic performance can be improved by selecting sweep and curve elaborately.


论文标题Experimental Study of Sweep and Dihedral Effects on Compressor Cascade Performance

作者Song Yanping, Zhao Guijie, Chen Fu, Wang Zhongqi

期刊名称6th European Turbomachinery Conference, Lille, France

期卷AFC-001_01

简单介绍In this paper a straight blade(STR), a forward-swept blade(SWF), and a blade combining forward sweep and positive dihedral(SCB) have been investigated in a linear compressor cascade at design and off-design incidence. The result shows that compared to STR, lower blade loading, lower diffusion factor and shorter axial static pressure diffusion are obtained near the endwall of SWF and SCB, which means lower loss near the endwalls of SWF and SCB despite the fact that SWF and SCB have higher loss at midspan. The accumulation of low-energy fluid, and thus flow separation occurring in the endwall/suction surface corner are avoided by pitchwise and spanwise surface static pressure gradient in SWF and SCB. The three-dimensional effect of SCB on the endwall boundary layer is stronger than that of STR and SWF. Further work should be done to seek the optimal matching between sweep and dihedral to take full advantage of the positive effect of sweep and dihedral on the endwall flow.


论文标题Experimental Study on the Aerodynamic Performance of Swept-Curved Blade

作者Zhao Guijie, Chen Fu, Song Yanping, Wang Zhongqi

期刊名称Chinese Journal of Aeronautics

期卷17(3):136-141

简单介绍Compared with a straight blade, a unique compressor blade integrated forward-swept and positive-curved stacking line is studied experimentally. Aerodynamic parameters of the two cascades are measured by a five-hole probe at different positions and ink trace flow visualization is conducted on blade surfaces. The result shows that the swept-curved cascade has lower endwall loss and higher midspan loss as compared with the straight cascade. However, lower loss is accompanied with lower diffusion factor. Opposite C shape static pressure distribution is established on the suction surface of the swept-curved blade, which is helpful for avoiding the accumulation of low energy fluid in the endwall corner region. Anyhow the studies support the conclusion that the swept-curved blade conduces to not only the reduction of overall loss but also the improvement of stable operation in the endwall corner region.


论文标题An Experimental Investigation on the Aerodynamic Performance and Flowfield Structure of a Film-Cooled Turbine Cascade

作者Chen Fu, Yang Hong

期刊名称ASME Turbo Expo 1999, Indianapolis USA

期卷ASME Paper 99-GT-280

简单介绍Experiments have been performed to study the aerodynamic performance and internal flows in a linear turbine cascade with air injection from various locations of the blade surface. Data were obtained by using pneumatic probe, static pressure taps and surface flow visualization techniques. The experimental results showed that the suction side injection would affect the development of the passage vortex significantly. The passage vortex was strengthened and pushed away from the injection surface, a triangular-shaped region uncovered by the injected air always existed on the suction surface due to the existence of the passage vortex. The passage vortex was weakened with air injection from pressure surface, which would cause a smaller amount of low momentum fluids to migrate into the comer region between suction surface and end wall. Although the scale and intensity of kidney-shaped vortices were different when air was injected from various positions, these vortices might always exist near the blade surface, mixing with mainflow in the flow passage and with wakes at the cascade exit while they moved downstream. The energy loss increased near the blade surface from which air was injected due mainly to the mixing process between mainflow and injected air, and to the formation of kidney-shaped vortices. In contrast to the pressure side injection, the changes of blade surface pressure distribution were more sensitive to the amount of injected air and the locations of injection holes for the suction side injection. In the great majority of cases, the surface pressure decreases owing to the existence of low-pressure zone downstream of the injection holes were more significant than the pressure increases caused by mainflow stagnation upstream of the holes.


出版物

出版物名称气体动力学基础

作者陈浮，宋彦萍，陈焕龙，刘华坪

出版时间,完成时间2013.08

出版社哈尔滨工业大学出版社

简单介绍本教材主要阐述了可压缩流体动力学的基本概念、规律和计算方法。全书共分九章：第一章介绍了流体力学、热力学的基础知识及概念，并对场论知识进行了了扼要阐述；第二章介绍了流体运动的基本方程组，并得到了上述方程组在一维流动假设条件下的不同形式；第三章介绍了滞止参数及气动函数的概念、计算公式；第四章介绍了膨胀波、激波；第五章介绍了一维定常、可压缩管道流动；第六章介绍了小扰动线性化理论及其应用；第七章介绍了超声速流动的特征线法；第八章介绍了气体的高超声速流动；第九章介绍了层流与湍流附面层。全书特别注意将矢量分析、场论等方法引入到气体动力学基本方程的推导中，以实现数学描述与物理内涵、力学原理三者之间的较为严格的统一，始终贯穿了基础、严谨、实用的方针，力图做到深入浅出。本书可作为高等工科院校热能与动力工程专业、飞行器动力工程专业等的专业基础教材，也可供飞行器设计、航空动力等从事气体动力学相关专业的科技人员参考。


出版物名称空气动力学基础

作者陈浮, 权晓波, 宋彦萍

出版时间,完成时间2015.01

出版社哈尔滨工业大学出版社

简单介绍本书较为全面的阐述了空气动力学的基本概念、规律和计算方法，尤其是将矢量分析、场论等方法引入到空气动力学基本方程的推导中，以实现数学描述、物理内涵与力学原理三者之间较为严格的统一。全书始终贯穿了基础、严谨、实用的方针，力图做到深入浅出。本书可作为高等工科院校有关专业的专业基础教材，尤其是飞行器设计、航空宇航动力、发射工程、航天运输等专业的教材，也可供相关专业的科技人员参考。